GB1219289A - Improvements in and relating to aircraft landing systems - Google Patents

Improvements in and relating to aircraft landing systems

Info

Publication number
GB1219289A
GB1219289A GB24763/67A GB2476367A GB1219289A GB 1219289 A GB1219289 A GB 1219289A GB 24763/67 A GB24763/67 A GB 24763/67A GB 2476367 A GB2476367 A GB 2476367A GB 1219289 A GB1219289 A GB 1219289A
Authority
GB
United Kingdom
Prior art keywords
aircraft
pitch attitude
signals
glide path
maintain
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB24763/67A
Inventor
Ian Alexander Watson
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Allard Way Holdings Ltd
Original Assignee
Elliott Brothers London Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Elliott Brothers London Ltd filed Critical Elliott Brothers London Ltd
Priority to GB24763/67A priority Critical patent/GB1219289A/en
Priority to FR1578662D priority patent/FR1578662A/fr
Publication of GB1219289A publication Critical patent/GB1219289A/en
Expired legal-status Critical Current

Links

Classifications

    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
    • G05D1/04—Control of altitude or depth
    • G05D1/06—Rate of change of altitude or depth
    • G05D1/0607—Rate of change of altitude or depth specially adapted for aircraft
    • G05D1/0653—Rate of change of altitude or depth specially adapted for aircraft during a phase of take-off or landing
    • G05D1/0676—Rate of change of altitude or depth specially adapted for aircraft during a phase of take-off or landing specially adapted for landing
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S1/00—Beacons or beacon systems transmitting signals having a characteristic or characteristics capable of being detected by non-directional receivers and defining directions, positions, or position lines fixed relatively to the beacon transmitters; Receivers co-operating therewith
    • G01S1/02—Beacons or beacon systems transmitting signals having a characteristic or characteristics capable of being detected by non-directional receivers and defining directions, positions, or position lines fixed relatively to the beacon transmitters; Receivers co-operating therewith using radio waves

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Automation & Control Theory (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Abstract

1,219,289. Automatic control of aircraft. ELLIOTT BROS. (LONDON) Ltd. May 23, 1968 [May 26, 1967J, No. 24763/67. Heading G3R. In an aircraft automatic landing system, signals from a radio receiver responsive to deviation from a glide path, with an integral component added, are combined with airspeed error signals applied through a multiplier stage to produce a resultant signal corresponding to the pitch attitude which the system is to maintain. As shown, signals from a glide slope radio receiver 1 are lagged at 2 and proportioned at 3. Integral and land-pass components derived at 5 and 6 are added at 7 and a signal dependent on airspeed deviation introduced through a multiplier 8. The resultant signal, representing the desired pitch attitude to maintain the aircraft on the glide path, is compared with actual pitch attitude and actual rate of change of pitch attitude signals at 9 so that any error is available at 11 to control the elevators and thus restore the aircraft to the glide path.
GB24763/67A 1967-05-26 1967-05-26 Improvements in and relating to aircraft landing systems Expired GB1219289A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB24763/67A GB1219289A (en) 1967-05-26 1967-05-26 Improvements in and relating to aircraft landing systems
FR1578662D FR1578662A (en) 1967-05-26 1968-09-03

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB24763/67A GB1219289A (en) 1967-05-26 1967-05-26 Improvements in and relating to aircraft landing systems

Publications (1)

Publication Number Publication Date
GB1219289A true GB1219289A (en) 1971-01-13

Family

ID=10216873

Family Applications (1)

Application Number Title Priority Date Filing Date
GB24763/67A Expired GB1219289A (en) 1967-05-26 1967-05-26 Improvements in and relating to aircraft landing systems

Country Status (2)

Country Link
FR (1) FR1578662A (en)
GB (1) GB1219289A (en)

Also Published As

Publication number Publication date
FR1578662A (en) 1969-08-14

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